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Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the ann

Methods of cooling a hot fluid in an annular duct of a gas turbine engine are provided. The method can include directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, and passing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered cooling channels. Additionally or alternatively, the method can include passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube; and passing a cooling fluid through the annular duct.

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1. A method of cooling a hot fluid in an annular duct of a gas turbine engine, comprising: directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, wherein the plurality of cooling channels are defined within a

1. A method of cooling a hot fluid in an annular duct of a gas turbine engine, comprising: directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, wherein the plurality of cooling channels are defined within a plurality of curvilinear plates that are radially layered within the annular duct, and wherein each curvilinear plate from the plurality of curvilinear plates traverses the annular duct from a radially inner portion to a radially outer portion with respect to a centerline of the annular duct, and further wherein each cooling channel from the plurality of cooling channels extends from a first opening along the radially inner portion of the curvilinear plate to a second opening along the radially inner portion of the curvilinear plate; andpassing a cooling fluid through the annular duct such that the cooling fluid passes between the radially layered plurality of curvilinear plates. 2. The method of claim 1, wherein the cooling fluid is generally flowing through the annular duct in an axial direction of the gas turbine engine. 3. The method of claim 1, wherein at least 90% of the cooling fluid flows through the heat transfer area of the annular duct. 4. The method of claim 1, wherein at least 95% of the cooling fluid flows through the heat transfer area of the annular duct. 5. The method of claim 1, wherein at least 99% of the cooling fluid flows through the heat transfer area of the annular duct. 6. The method of claim 1 wherein a gap is defined between radially adjacent curvilinear plates through which the cooling fluid flows. 7. The method of claim 1, wherein the cooling fluid is fan air of the gas turbine engine, and wherein the hot fluid is bleed air of the gas turbine engine. 8. A method of cooling a hot fluid in an annular duct of a gas turbine engine, comprising: directing the hot fluid through a plurality of cooling channels that are radially layered within the annular duct to define a heat transfer area, wherein the plurality of cooling channels are defined within a plurality of curvilinear plates that are radially layered within the annular duct, and wherein each curvilinear plate from the plurality of curvilinear plates traverses the annular duct from a radially inner portion to a radially outer portion with respect to a centerline of the annular duct, and further wherein each cooling channel from the plurality of cooling channels extends from a first opening along the radially inner portion of the curvilinear plate to a second opening along the radially inner portion of the curvilinear plate; andpassing a cooling fluid through the annular duct in an axial direction of the gas turbine engine, wherein at least 90% of the cooling fluid flows through the heat transfer area of the annular duct. 9. The method of claim 8, wherein at least 95% of the cooling fluid flows through the heat transfer area of the annular duct. 10. The method of claim 8, wherein at least 99% of the cooling fluid flows through the heat transfer area of the annular duct. 11. The method of claim 8, wherein each of the plurality of curvilinear plates is supported structurally so that thermal expansion of each of the plurality of curvilinear plates relative to the annular duct is unrestrained in at least one direction. 12. The method of claim 8, wherein the cooling fluid is fan air of the gas turbine engine, and wherein the hot fluid is bleed air of the gas turbine engine. 13. A method of cooling a hot fluid in an annular duct of a gas turbine engine, comprising: passing the hot fluid into a first inner radial tube, through a plurality of cooling channels defined within a plurality of curvilinear plates that are radially layered within the annular duct, and into a second inner radial tube, wherein each curvilinear plate from the plurality of curvilinear plates traverses the annular duct from a radially inner portion to a radially outer portion with respect to a centerline of the annular duct, wherein a first opening is in fluid communication with the first inner radial tube along the radially inner portion of the curvilinear plate, and wherein a second opening is in fluid communication with the second inner radial tube along the radially inner portion of the curvilinear plate; and passing a cooling fluid through the annular duct. 14. The method of claim 13, wherein each of the plurality of curvilinear plates comprises an inner plate defining a plurality of first grooves and an outer plate defining a plurality of second grooves, wherein the outer plate is attached to the inner plate with the plurality of first grooves and the plurality of second grooves substantially aligned to define the plurality of cooling channels therebetween. 15. The method of claim 13, wherein each of the plurality of curvilinear plates further comprises an integral wall positioned between the inner plate and the outer plate such that the hot fluid passes through a first passageway and a second passageway within the plurality of cooling channels. 16. The method of claim 15, wherein the outer plate of each of the plurality of curvilinear plates defines a chord length measured as a shortest distance from a first end to a second end, and wherein the outer plate defines an are length measured across its outer surface from the first end to the second end, and further wherein the are length is about 105% to about 150% of the chord length. 17. The method of claim 13, wherein the cooling fluid is fan air of the gas turbine engine, and wherein the hot fluid is bleed air of the gas turbine engine. 18. The method of claim 13, wherein at least 90% of the cooling fluid flows through a heat transfer area of the annular duct defined radially outward from the first inner radial tube and the second inner radial tube to an outer support structure.